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Flight unit control system, flight control device including such a system, and use of such a system

  • US 8,820,172 B2
  • Filed: 05/05/2011
  • Issued: 09/02/2014
  • Est. Priority Date: 05/06/2010
  • Status: Active Grant
First Claim
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1. A flight unit control system, comprising at least one instrumented fastening bolt connecting an aircraft carrier structure and a load path, the at least one instrumented bolt having at least one measurement area for detecting that the load path is under load, the system comprising fastening means for locking the at least one instrumented bolt in position relative to the aircraft carrier structure and to the load path without stressing the at least one instrumented bolt in the at least one measurement area, neither in tension nor in torsion, wherein the at least one measurement area of the at least one instrumented bolt includes:

  • two cavities which are opposite each other in relation to an axis and separated from each other along a transverse axis by a thin wall that is deformed under a shear stress applied to the at least one instrumented bolt, andat least one strain gauge which is placed in a bottom of one of the cavities against the thin wall, the at least one strain gauge detecting a deformation of the thin wall,and in that the fastening means includes;

    a fastening plate which is positioned at a threaded end of the at least one instrumented bolt, bearing against one of the aircraft carrier structure and the load path, and which extends perpendicularly to the axis of the at least one instrumented bolt, anda nut which is placed on the threaded end of the at least one instrumented bolt and immobilizes the at least one instrumented bolt relative to the one of the aircraft carrier structure and the load path against which the fastening plate bears.

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